公开(公告)号：US06751962B1

公开(公告)日：2004-06-22

申请号：US09521413

申请日：2000-03-08

申请人： Masamitsu Kuwabara ,  Yasuoki Tomita ,  Kiyoshi Suenaga ,  Masahito Kataoka ,  Yoshichika Sato ,  Koji Watanabe

发明人： Masamitsu Kuwabara ,  Yasuoki Tomita ,  Kiyoshi Suenaga ,  Masahito Kataoka ,  Yoshichika Sato ,  Koji Watanabe

IPC分类号： F23R360

CPC分类号： F01D9/023 ,  F23R3/60

摘要： In a tail tube seal structure of gas turbine, a U-shaped groove is provided at one side of a tail tube seal where a flange of a tail tube outlet is fitted, and a pi-shaped groove is provided at other side of the tail tube seal where a gas pass side flange end is fitted, thereby composing the seal of the connection area. Inclined cooling holes are drilled in the tail tube seal in addition to the cooling holes existing conventionally. The cooling air flows in from the inclined holes and cools the gas pass side of the groove due to the film effect. Therefore, the difference in thermal expansion between the groove and flange end is decreased, the wear of this area is decreased, and the reliability of the seal is enhanced.

摘要翻译： 在燃气轮机的尾管密封结构中，在尾管密封件的一侧设置有U形槽，其中尾管出口的凸缘被装配，并且在该尾部的另一侧设置有一个pi形槽 管密封件，其中安装有气体通过侧凸缘端，从而构成连接区域的密封。 除了常规存在的冷却孔之外，还在尾管密封件中钻出倾斜的冷却孔。 冷却空气从倾斜孔流入，由于膜效应而冷却槽的气体通过侧。 因此，凹槽和凸缘端之间的热膨胀差异减小，该区域的磨损减小，并且密封件的可靠性提高。

公开(公告)号：US06270311B1

公开(公告)日：2001-08-07

申请号：US09518644

申请日：2000-03-03

申请人： Masamitsu Kuwabara ,  Yasuoki Tomita ,  Kiyoshi Suenaga ,  Masahito Kataoka ,  Yoshichika Sato ,  Koji Watanabe

发明人： Masamitsu Kuwabara ,  Yasuoki Tomita ,  Kiyoshi Suenaga ,  Masahito Kataoka ,  Yoshichika Sato ,  Koji Watanabe

IPC分类号： F01D100

CPC分类号： F01D11/005 ,  F05D2260/202

摘要： In gas turbine split rings, end faces having bent surfaces are formed in flanges. Adjoining split rings are coupled together with a groove therebetween to form a cylindrical split ring. Notches are formed in the flanges. These notches are sealed by inserting a seal plate into the notches of adjoining split rings. A hole for passing cooling air is drilled obliquely in the flange. Cooling air is allowed to flow out along the direction of rotation (of the turbine). This cooling air cools the outlet of the groove due to the effect of film cooling. Because of such cooling, high temperature gas is prevented from staying in this area, cooling effect is enhanced, and hence burning of the end portions can be prevented.

摘要翻译： 在燃气涡轮分裂环中，具有弯曲表面的端面形成为凸缘。 相邻的开口环与它们之间的槽耦合在一起以形成圆柱形的开口环。 在法兰上形成凹口。 这些凹口通过将密封板插入相邻的分隔环的凹口中而被密封。 用于通过冷却空气的孔倾斜地在法兰上钻出。 允许冷却空气沿着涡轮机的旋转方向流出。 由于薄膜冷却的作用，该冷却空气冷却槽的出口。 由于这样的冷却，防止高温气体停留在该区域，因此冷却效果增强，因此可以防止端部的燃烧。

公开(公告)号：US06290462B1

公开(公告)日：2001-09-18

申请号：US09272559

申请日：1999-03-19

申请人： Tatsuo Ishiguro ,  Koji Watanabe ,  Masaaki Matsuura ,  Kenichiro Takeishi ,  Junichiro Masada ,  Yasuoki Tomita ,  Kiyoshi Suenaga

发明人： Tatsuo Ishiguro ,  Koji Watanabe ,  Masaaki Matsuura ,  Kenichiro Takeishi ,  Junichiro Masada ,  Yasuoki Tomita ,  Kiyoshi Suenaga

IPC分类号： F01D1100

CPC分类号： F01D5/187 ,  F05D2250/185 ,  F05D2260/2212

摘要： A gas turbine cooled blade is constructed without an increase in the number of parts or time requirements, in which seal air is maintained at a lower temperature with the heat exchange rate being suppressed, and the heat transfer rate of the cooling medium in cooling passage is enhanced. A plurality of cooling passages (A, B, C, D, E) is provided in a blade, and the first row cooling passage (A) is covered at the blade inner and outer peripheries and communicates with the second row cooling passage (B) through communication holes (6) and with the main flow gas path through film cooling holes (7). The second row cooling passage (B) communicates with the blade inner peripheral cavity (10) to form a seal air supply passage. A plurality of ribs (31) are disposed on the inner wall of cooling passage (22) with a predetermined pitch (P). The ribs are arranged alternately and are inclined against cooling medium flow with respective higher first end contacting lower side faces of an immediately upstream rib at a position on both side portions of cooling passage (22). High heat transfer rate areas are formed on both side portions of cooling passage (22), and the average heat transfer rate in cooling passage is enhanced.

摘要翻译： 在不增加部件或时间要求的情况下构建燃气轮机冷却叶片，其中密封空气在热交换率被抑制下保持在较低温度，并且冷却通道中的冷却介质的传热速率为 增强。 多个冷却通道（A，B，C，D，E）设置在叶片中，第一排冷却通道（A）被覆盖在叶片的内周和外周，并与第二排冷却通道 ）通过连通孔（6）并且主流动气体通道通过膜冷却孔（7）。 第二排冷却通道（B）与叶片内周腔（10）连通，形成密封空气供给通道。 多个肋（31）以预定的间距（P）设置在冷却通道（22）的内壁上。 这些肋交替布置并且相对于冷却介质流倾斜，并且在冷却通道（22）的两侧部分的位置处，相应较高的第一端接触紧紧上游的肋的下侧面。 在冷却通道（22）的两侧形成有高的传热率区域，并且冷却通路的平均传热率提高。

公开(公告)号：US06196799B1

公开(公告)日：2001-03-06

申请号：US09252064

申请日：1999-02-18

申请人： Ichiro Fukue ,  Eiji Akita ,  Kiyoshi Suenaga ,  Yasuoki Tomita ,  Koji Watanabe

发明人： Ichiro Fukue ,  Eiji Akita ,  Kiyoshi Suenaga ,  Yasuoki Tomita ,  Koji Watanabe

IPC分类号： F01D518

CPC分类号： F01D5/187 ,  F01D5/186 ,  F05D2240/81

摘要： A gas turbine moving blade platform having a simplified cooling structure for effecting uniform cooling of the platform. The platform (1) includes cavities (2, 3, 4) and an impingement plate (11) provided below the cavities (2, 3, 4). A cooling hole (5) communicates with cavity (2), cooling hole (6) communicated with cavity (3) and cooling holes (7, 8) communicate with cavity (4) and all of the cooling holes pass through the platform (1) at an inclined angle. Cooling air (70) flows into the cavities (2, 3, 4) through holes (12) in the impingement plate (11) for effecting impingement cooling of platform (1) plane portion. The cooling air (70) further flows through the cooling holes (5, 6, 7) to blow outside angularly upward for cooling peripheral portions of the platform. Thus, the platform is cooled uniformly, no lengthy and complicated cooling passage is provided, and workability is enhanced.

摘要翻译： 一种具有简化冷却结构的燃气轮机动叶片平台，用于实现平台的均匀冷却。 平台（1）包括空腔（2,3,4）和设置在空腔（2,3,4）下方的冲击板）。 冷却孔（5）与空腔（2）连通，与空腔（3）连通的冷却孔（6）和冷却孔（7,8）与空腔（4）连通，所有的冷却孔都通过平台 ）。 冷却空气（70）通过冲击板（11）中的孔（12）流入空腔（2,3,4），以实现平台（1）平面部分的冲击冷却。 冷却空气（70）进一步流过冷却孔（5,6,7）以向外侧向外侧吹出以冷却平台的周边部分。 因此，平台被均匀地冷却，没有设置冗长且复杂的冷却通道，并且可加工性得到提高。

公开(公告)号：US06092991A

公开(公告)日：2000-07-25

申请号：US35500

申请日：1998-03-05

申请人： Yasuoki Tomita ,  Taku Ichiryu ,  Kiyoshi Suenaga

发明人： Yasuoki Tomita ,  Taku Ichiryu ,  Kiyoshi Suenaga

IPC分类号： F01D5/18

CPC分类号： F01D5/187 ,  F05D2240/81 ,  F05D2260/2212

摘要： A gas turbine blade having a platform and a turbine wheel plate, in which cooling passages are arranged in a plurality of rows and connected to one another in a blade trunk section of a moving blade and a supply-side passage and a discharge-side passage are formed in a blade root section. The gas turbine blade comprises a pocket having an inlet and an outlet formed in the blade root section. The supply-side passage is connected to one of the cooling passages and the inlet of the pocket, the outlet of the pocket is connected to another of the cooling passages, and the discharge-side passage is connected to one of the cooling passages other than the ones connected individually to the supply-side passage and the pocket.

摘要翻译： 一种具有平台和涡轮机叶轮板的燃气轮机叶片，其中，冷却通道以多行排列并且在动叶片的叶片主干部分和供给侧通道和排出侧通道中彼此连接 形成在叶片根部中。 燃气轮机叶片包括具有形成在叶片根部中的入口和出口的袋。 供给侧通路连接到一个冷却通道和袋的入口，口袋的出口连接到另一个冷却通道，排出侧通道连接到除了 它们分别连接到供应侧通道和口袋。

公开(公告)号：US06196798B1

公开(公告)日：2001-03-06

申请号：US09242330

申请日：1999-02-11

申请人： Hiroki Fukuno ,  Yasuoki Tomita ,  Shigeyuki Maeda ,  Yukihiro Hashimoto ,  Kiyoshi Suenaga

发明人： Hiroki Fukuno ,  Yasuoki Tomita ,  Shigeyuki Maeda ,  Yukihiro Hashimoto ,  Kiyoshi Suenaga

IPC分类号： F01D518

CPC分类号： F01D5/186 ,  F01D5/18

摘要： A number of air-transpiration holes (4) are provided at a leading edge portion (2) of a cooled blade (1). Cooling air flowing through a cooling air passage (15) formed inside of the blade blows out to the blade surface of the leading edge portion (2) of the cooled blade (1) by way of the air-transpiration holes (4), to thereby shower-head cool the surface of the leading edge portion (2). The air-transpiration holes (4) are formed so as to extend substantially orthogonal to the leading edge surface of the cooled blade (1) such that the acute-angled portions are eliminated, whereby thermal stress is reduced and cracking is prevented.

摘要翻译： 在冷却叶片（1）的前缘部分（2）处设置有多个空气蒸发孔（4）。 流过形成在叶片内的冷却风道（15）的冷却空气通过空气蒸发孔（4）吹向冷却叶片（1）的前缘部（2）的叶片表面，至 从而喷淋头对前缘部分（2）的表面进行冷却。 空气蒸发孔（4）形成为基本上垂直于冷却叶片（1）的前缘表面延伸，使得锐角部分被消除，从而减少热应力并防止开裂。

公开(公告)号：US06196791B1

公开(公告)日：2001-03-06

申请号：US09202951

申请日：1998-12-23

申请人： Yasuoki Tomita ,  Hiroki Fukuno ,  Sunao Aoki ,  Kiyoshi Suenaga

发明人： Yasuoki Tomita ,  Hiroki Fukuno ,  Sunao Aoki ,  Kiyoshi Suenaga

IPC分类号： F01D518

CPC分类号： F02C7/12 ,  F01D5/081 ,  F01D5/18

摘要： In gas turbine cooled moving blade, a cooling air passage is made shortest and temperature elevation and pressure drop of the cooling air are suppressed. The cooling air passage (16) is bored in a turbine cylinder wall (15) located below a first stage stationary blade (11). The cooling air passage (16) communicates at one end (16a) with a turbine cylinder and at the other end (16b) with a space (13) between the stationary blade and the moving blade. The passage (16) is directed to an air inflow hole (6) provided in a shank portion (4) of a lower portion of a platform (2) of the moving blade (1). Cooling air is jetted from the cooling air passage (16) toward the air inflow hole (6) so as to flow into the shank portion (4) and then into the moving blade (1) for cooling thereof. An axis (17) of the cooling air passage (16) is directed so as to deviate in a rotational circumferential direction by an angle determined by the velocity of the cooling air jetted from the cooling air passage (16) and the rotational velocity of the moving blade (1) from position of the air inflow hole when the moving blade (1) stands still in row with the stationary blade (11) in rotor axial direction. Thus, the cooling air can be jetted in an optimal direction with the shortest distance, and the temperature elevation and pressure drop of the cooling air can be suppressed to minimum.

摘要翻译： 在燃气轮机冷却动叶片中，冷却空气通道最短，并且冷却空气的温度升高和压降被抑制。 冷却空气通道（16）在位于第一级固定叶片（11）下方的涡轮机气缸壁（15）中钻孔。 冷却空气通道（16）在一端（16a）与涡轮机气缸连通，另一端（16b）在固定叶片和动叶片之间具有空间（13）。 通道（16）被引导到设置在活动叶片（1）的平台（2）的下部的柄部分（4）中的空气流入孔（6）。 冷却空气从冷却空气通路（16）向空气流入孔（6）喷射，从而流入柄部（4），然后进入动叶片（1）进行冷却。 冷却空气通路16的轴线（17）被引导为以从冷却空气通路（16）喷射的冷却空气的速度和旋转速度确定的旋转圆周方向偏离角度 当动叶片（1）在转子轴向与静叶片（11）静置时，从动空气流入孔的位置移动叶片（1）。 因此，可以以最短的距离沿最佳方向喷射冷却空气，并且可以将冷却空气的温度升高和压降降低到最小。

公开(公告)号：US06190130B1

公开(公告)日：2001-02-20

申请号：US09255793

申请日：1999-02-23

申请人： Ichiro Fukue ,  Eiji Akita ,  Kiyoshi Suenaga ,  Yasuoki Tomita

发明人： Ichiro Fukue ,  Eiji Akita ,  Kiyoshi Suenaga ,  Yasuoki Tomita

IPC分类号： F01D518

CPC分类号： F01D5/187 ,  F05D2240/81

摘要： A gas turbine moving blade platform having a simplified platform cooling structure. A cooling effect of the platform side end portions is increased resulting in uniform cooling of the entire platform. Cooling passages (2, 3) are bored in the platform (1) front portion so as to communicate with a cooling air passage (52) of the moving blade (51) and open at both platform side end surfaces. The openings are closed by inserting covers (2a, 2b) therein. Cooling passages (6, 4) are bored in platform (1) side end portions so as to communicate with the front end cooling passages (2, 3), respectively, and open in the platform rear end surface. A plurality of cooling holes (5) are bored so as to communicate with the cooling passage (4) and open at the platform side end surface. Thus, the entire platform is cooled uniformly and the platform side portions are cooled by the cooling holes (5) so that an effective cooling performance is ensured and also the workability of the cooling lines is enhanced.

摘要翻译： 具有简化的平台冷却结构的燃气轮机动叶片平台。 平台侧端部的冷却效果增加，导致整个平台的均匀冷却。 在平台（1）的前部分中钻出冷却通道（2,3），以便与活动叶片（51）的冷却空气通道（52）连通并在两个平台侧端面处打开。 通过将盖（2a，2b）插入其中来封闭开口。 平台（1）的侧端部分分别将冷却通道（6,4）与前端冷却通道（2,3）连通，并在平台后端面开口。 多个冷却孔（5）钻孔，以与冷却通道（4）连通并在平台侧端面打开。 因此，整个平台被均匀地冷却，并且平台侧部分被冷却孔（5）冷却，从而确保了有效的冷却性能，并且还提高了冷却管线的可加工性。

公开(公告)号：US6152695A

公开(公告)日：2000-11-28

申请号：US243821

申请日：1999-02-03

申请人： Ichiro Fukue ,  Eiji Akita ,  Kiyoshi Suenaga ,  Yasuoki Tomita

发明人： Ichiro Fukue ,  Eiji Akita ,  Kiyoshi Suenaga ,  Yasuoki Tomita

IPC分类号： F01D5/18 ,  F01D5/20 ,  F01D5/22

CPC分类号： F01D5/187 ,  F01D5/225 ,  F05D2240/81 ,  F05D2260/22141

摘要： In a gas turbine moving blade 1, the convection of cooling air is promoted to enhance the heat transfer rate, the cooling effect of a shroud 2 is enhanced and the entire cooling effect of the blade is enhanced. An inner cavity 10 is formed in the blade over the entire length thereof. A multiplicity of pin fins 5 are provided in the inner cavity, being fixed to wall thereof. An enlarged cavity 6 is formed in the shroud 2 of a terminal end of the blade 1. Cooling air entering the inner cavity 10 of the blade 1 flows into the enlarged cavity 6 and flows out of the shroud 2 downwardly through holes 7 of a peripheral portion of the enlarged cavity 6. The entire portion of the shroud 2 is cooled uniformly, and the cooling effect of the entire blade is enhanced by an enhanced heat transfer rate in the blade and by uniform cooling of the entire shroud.

摘要翻译： 在燃气轮机动叶片1中，促进冷却空气的对流，提高传热速度，提高护罩2的冷却效果，提高叶片的整体冷却效果。 在叶片的整个长度上形成内腔10。 多个销翅片5设置在内腔中，固定在其壁上。 在叶片1的末端的护罩2中形成有扩大的空腔6.进入叶片1的内腔10的冷却空气流入扩大空腔6，并通过周边的孔7向下流出护罩2 扩大的腔体6的部分。护罩2的整个部分被均匀地冷却，并且整个刀片的冷却效果通过增加叶片中的传热速率和整个护罩的均匀冷却来增强。

公开(公告)号：US6142730A

公开(公告)日：2000-11-07

申请号：US202690

申请日：1998-12-21

申请人： Yasuoki Tomita ,  Kenichi Arase ,  Hiroki Fukuno ,  Hideki Murata ,  Kiyoshi Suenaga ,  Tsuyoshi Kitamura

发明人： Yasuoki Tomita ,  Kenichi Arase ,  Hiroki Fukuno ,  Hideki Murata ,  Kiyoshi Suenaga ,  Tsuyoshi Kitamura

IPC分类号： F01D9/02 ,  F01D5/18 ,  F01D9/04 ,  F01D9/06 ,  F02C7/18

CPC分类号： F01D9/065 ,  F01D5/187 ,  F05D2240/81 ,  Y02T50/676

摘要： In a cooled gas turbine stationary blade, both steam cooling and air cooling are utilized to reduce the amount of cooling air. In the stationary blade having outer and inner shrouds 1, 21 and steam passages 10A, 10B, 10C, 10D and 10E which are communicated with each other and in which a sealing air feed tube 2 passes through a central portion thereof, steam covers 3, 4 are provided in the outer shroud 1, and steam S is introduced from a steam feed port 5. The steam S passes through serpentine passages 10A to 10E and is recovered from the steam outlet 12 after cooling the central portion of the outer shroud 1 by means of an impingement plate 8. A portion of the steam of the passage 10A is introduced from the impingement plate 25 to a steam sump 24 to cool the central portion of the inner shroud 21 and pass through the passage 10D to be recovered from the steam outlet port 12. On the other hand, cooling air is fed from cooling air feed ports 6 and 26 to peripheral portions of the outer and inner shrouds 1, 21, and is discharged to the outside from the rear sides thereof, respectively, and the cooling air is further fed from a cooling air feeding port 7 to the passage 10E on the rear edge of the blade to cool the rear edge of the blade. Only the narrow portions where it is difficult for the steam to pass are air-cooled to thereby reduce the amount of the cooling air.

摘要翻译： PCT No.PCT / JP98 / 01959 Sec。 371 1998年12月21日第 102（e）日期1998年12月21日PCT提交1998年4月28日PCT公布。 公开号WO98 / 50685 PCT 日期1998年11月12日在冷却式燃气轮机固定叶片中，蒸汽冷却和空气冷却都用于减少冷却空气的量。 在具有彼此连通并且密封空气供给管2穿过其中心部分的外护罩1和21以及蒸汽通道10A，10B，10C，10D和10E的固定刀片中，蒸汽罩3， 4设置在外护罩1中，并且蒸汽S从蒸汽供给口5引入。蒸汽S通过蛇形通道10A至10E，并且在冷却外护罩1的中心部分之后从蒸汽出口12回收， 冲击板8的装置。通道10A的蒸汽的一部分从冲击板25引入蒸汽槽24，以冷却内护罩21的中心部分，并通过通道10D以从蒸汽中回收 另一方面，冷却空气从冷却空气供给口6和26被供给到外护罩1和外护罩21的周边部分，并且分别从其后侧排出到外部， 冷却空气很冷 她从冷却空气供给口7进入叶片后缘的通道10E，以冷却叶片的后边缘。 只有蒸汽难以通过的狭窄部分被空气冷却，从而减少冷却空气的量。